Staged fuel and air injection in combustion systems of gas turbines

Hughes, Michael John; Berry, Jonathan Dwight

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Title: Staged fuel and air injection in combustion systems of gas turbines

Abstract

A gas turbine including a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus, and a third radial wall formed about the outer radial wall that forms an outer flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section corresponding to the aftward annulus section and a forward intake section corresponding to the forward annulus section. The air directing structure may include a switchback coolant flowpath to direct air from the compressor discharge cavity to the staged injector. The switchback coolant flowpath may include an upstream section through the flow annulus, and a downstream section through the outer flow annulus.

Inventors:: Hughes, Michael John; Berry, Jonathan Dwight

Issue Date:: Tue Apr 10 00:00:00 EDT 2018

Research Org.:: General Electric Co., Schenectady, NY (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1434521

Patent Number(s):: 9938903

Application Number:: 14/978,019

Assignee:: General Electric Company (Schenectady, NY)

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS

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F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C3/04 - having a turbine driving a compressor
F02C7/12 - Cooling of plants
F02C7/18 - the medium being gaseous, e.g. air {
F02C7/222 - {Fuel flow conduits, e.g. manifolds}

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R2900/03043 - Convection cooled combustion chamber walls with means for guiding the cooling air flow
F23R2900/03044 - Impingement cooled combustion chamber walls or subassemblies
F23R3/002 - {Wall structures
F23R3/04 - Air inlet arrangements
F23R3/286 - {having fuel-air premixing devices
F23R3/346 - {for staged combustion}
F23R3/46 - Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings
F23R3/50 - Combustion chambers comprising an annular flame tube within an annular casing

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DOE Contract Number:: FC26-05NT42643

Resource Type:: Patent

Resource Relation:: Patent File Date: 2015 Dec 22

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS

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                    Hughes, Michael John, and Berry, Jonathan Dwight. Staged fuel and air injection in combustion systems of gas turbines.  United States: N. p., 2018. 
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                    Hughes, Michael John, & Berry, Jonathan Dwight. Staged fuel and air injection in combustion systems of gas turbines.  United States.

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                    Hughes, Michael John, and Berry, Jonathan Dwight. Tue .  
        "Staged fuel and air injection in combustion systems of gas turbines".  United States.  https://www.osti.gov/servlets/purl/1434521.

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@article{osti_1434521,

  title        = {Staged fuel and air injection in combustion systems of gas turbines},

  author       = {Hughes, Michael John and Berry, Jonathan Dwight},

  abstractNote = {A gas turbine including a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus, and a third radial wall formed about the outer radial wall that forms an outer flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section corresponding to the aftward annulus section and a forward intake section corresponding to the forward annulus section. The air directing structure may include a switchback coolant flowpath to direct air from the compressor discharge cavity to the staged injector. The switchback coolant flowpath may include an upstream section through the flow annulus, and a downstream section through the outer flow annulus.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {Tue Apr 10 00:00:00 EDT 2018},

  month        = {Tue Apr 10 00:00:00 EDT 2018}

}

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